A transonic compressor stage has been designed for the NavalPostgraduate School Turbopropulsion Laboratory. The design reliedheavily on CFD techniques while minimizing conventional empiricaldesign methods. The low aspect ratio (1.2) rotor has been designedfor a specific head ratio of .25 and a tip relative inlet Mach numberof 1.3. Overall stage pressure ratio is 1.56. The rotor was designedusing an Euler code augmented by a distributed body force model toaccount for viscous effects. This provided a relatively quick-runningdesign tool, and was used for both rotor and stator calculations. Theinitial stator sections were sized using a compressible, cascade panelcode. In addition to being used as a case study for teachingpurposes, the compressor stage will be used as a research stage.Detailed measurements, including non-intrusive LDV, will becompared with the design computations, and with the results of otherCFD codes, as a means of assessing and improving thecomputational codes as design tools.
展开▼
